Adhesion of particulate matters to the burner accompanying combustion in a lean-combustion gas turbine combustor is suppressed, and the structural reliability is improved. In a gas turbine combustor including: a tubular liner that forms a combustion chamber; and a burner including an air hole plate that is arranged at an inlet of the liner and includes a plurality of air holes for guiding compressed air to the combustion chamber, and a plurality of fuel nozzles that are arranged on a side opposite to the combustion chamber with the air hole plate being sandwiched therebetween, the plurality of fuel nozzles each injecting a fuel toward a corresponding air hole, the air holes and the fuel nozzles forming a plurality of concentric annular lines, a plurality of small holes having opening diameters smaller than those of the air holes are provided through the air hole plate such that the plurality of small holes are positioned in an inner area of an innermost annular line of the air holes.

An annular combustor is disclosed in which free-vortices are generated which: enhance fuel air mixing, recirculate the air, provide cooling for the combustor walls, and provide low emissions and a substantially uniform exit temperature profile. The combustor is provided fuel and air through a plurality of fuel injectors which atomizes the fuel and promote individual vortices emanating from each injector. The combustor includes an annular prechamber, an annular main chamber, and an annular dilution zone. A first swirler is provided on the inner side of the annular prechamber and a second swirler on the outer side of the annular prechamber, the swirlers causing flow to rotate in mutually opposite directions to intensify the vortices imposed by the injectors. The vortices cause a pressure depression to promote some backflow that enhance mixing to: promote complete combustion, produce low emissions, and provide cooling.

The present invention is a downstream plate which is provided on a downstream side of an upstream plate includes an air inlet into which cooling air is introduced from a cooling air introduction pipe and a cooling flow path which extends in a direction along a surface of the downstream plate from the air inlet so as to avoid a premix tube and through which cooling air flows.

A free-vortex combustor is disclosed that generates vortices which: enhance fuel air mixing, recirculate the air, provide cooling for the combustor walls, and provide low emissions and a substantially uniform exit temperature profile. The combustor is provided fuel or fuel and air through a fuel injector which atomizes the fuel. A first air swirler couples to the fuel injector with a prechamber wall abutting the first swirler. A second swirler abuts a downstream end of the prechamber wall. And, a main chamber abuts the second swirler. Each of the first and second swirlers have features that cause the flow to create a vortex in the prechamber and main chamber, respectively. The features creating the swirl are blades or angled orifices. The vortex causes a pressure depression along the centerline and causes backflow along the centerline that improves mixing and improves cooling.

An annular combustor is disclosed in which free-vortices are generated which: enhance fuel air mixing, recirculate the air, provide cooling for the combustor walls, and provide low emissions and a substantially uniform exit temperature profile. The combustor is provided fuel and air through a plurality of fuel injectors which atomizes the fuel and promote individual vortices emanating from each injector. The combustor includes an annular prechamber, an annular main chamber, and an annular dilution zone. A first swirler is provided on the inner side of the annular prechamber and a second swirler on the outer side of the annular prechamber, the swirlers causing flow to rotate in mutually opposite directions to intensify the vortices imposed by the injectors. The vortices cause a pressure depression to promote some backflow that enhance mixing to: promote complete combustion, produce low emissions, and provide cooling.

To provide a gas turbine combustor that can suppress a generation amount of NOx and maintain a flame holding property, while suppressing burn damage around a pilot nozzle including the pilot nozzle. A gas turbine combustor includes a pilot nozzle that can inject fuel F and cooling air A for cooling a nozzle tip, a flow regulating valve that can adjust a flow rate of cooling air to be supplied to the pilot nozzle, a detection sensor that detects a combustion state of fuel, and a control device that controls the flow regulating valve based on a detection result of the detection sensor.

The present invention relates to methods and systems for controlling a combustion reaction and the products thereof. One embodiment includes a combustion control system having an oxygen supply stream and a high concentration carbon dioxide stream, mixing the streams to form an oxygenation stream substantially comprising oxygen and CO2 and having an oxygen to CO2 ratio, then mixing the oxygenation stream with a combustion fuel stream and combusting in a combustor to generate a combustion products stream having a temperature detected by a temperature sensor, the data from which is used to control the flow a carbon dioxide diluent stream to produce a desired temperature of combustion. The system may also include a control system configured to regulate the flow of the oxygen supply stream based on the flow rate and composition of the combustion fuel stream. The system may also include a gas turbine with an expander and having a load and a load controller in a feedback arrangement. Other embodiments include a hydrocarbon analyzer and multiple fuel streams that may be combined to form the combustion fuel stream.

Proposed are a jet nozzle, and a combustor and a gas turbine including the jet nozzle. The jet nozzle is formed on an inner surface of a combustor to supply fluid into an interior of a liner of the combustor in a direction intersecting with a progress direction of combustion gases primarily combusted in a combustion chamber in the interior of the liner. The jet nozzle includes a fluid inlet, through which fluid is externally introduced, and a fluid outlet including a first fluid outlet member, through which a portion of the fluid introduced through the fluid inlet is discharged so as to be rotated in one direction, and a second fluid outlet member, through which the rest of the fluid is discharged so as to be rotated in a direction different from the rotation direction of the fluid discharged from the first fluid outlet member.

A combustion chamber for an aircraft turbomachine includes an annular chamber end wall and an annular row of injection systems mounted in the annular chamber end wall. Each injection system includes at least one air inlet swirler and a main fuel injection nozzle to output a fuel stream centered on an injection axis and including a central recirculation zone and a corner recirculation zone extending as an annulus around the central recirculation zone chamber. The combustion chamber also includes a plurality of additional fuel injection devices mounted in the chamber end wall to inject fuel directly into the corresponding corner recirculation zones produced by the corresponding injection systems at an operating speed less than or equal to the idling speed.

A jet burner has a hot-gas side, which faces toward a combustion chamber during operation, and a cold-gas side, which faces away from a combustion chamber, including a base plate on which there are arranged multiple jet nozzles, wherein the base plate has at least one cooling duct, wherein the at least one cooling duct issues into a burner stage which comprises a pilot burner arranged on the base plate.